34580 Federal Register / Vol. 63, No. 122 /Thursday, June 25, 1998 /Rules and Regulations

This incorporation by reference was

approved by the Director of the Federal

Register in accordance with 5 U.S.C. 552(a)

and 1 CFR part 51. Copies may be obtained

from Rolls-Royce, PO Box 3, Filton, Bristol

BS12 7QE, England; telephone 01-17–979–

1234, fax 01–17–979–7575. Copies may be

inspected at the FAA, New England Region,

Office of the Regional Counsel, 12 New

England Executive Park, Burlington, MA; or

at the Office of the Federal Register, 800

North Capitol Street, NW., suite 700,

Washington, DC.

(g) This amendment becomes effective on

July 10, 1998.

Issued in Burlington, Massachusetts, on

June 12, 1998.

Jay J. Pardee,

Manager, Engine and Propeller Directorate,

Aircraft Certification Service.

[FR Doc. 98–16467 Filed 6–24–98; 8:45 am]

BILLING CODE 4910–13–U

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 97–NM–257–AD; Amendment

39–10624; AD 98–13–33]

RIN 2120–AA64

Airworthiness Directives; Airbus Model

A300, A300–600, and A310 Series

Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment adopts a

new airworthiness directive (AD),

applicable to all Airbus Model A300,

A300–600, and A310 series airplanes,

that requires repetitive tests to detect

desynchronization of the rudder servo

actuators, and adjustment or

replacement of the spring rods of the

rudder servo actuators, if necessary. For

certain airplanes, this AD also requires

repetitive inspections to detect cracking

of the rudder attachments, and repair, if

necessary; or modification of the rudder

attachments. This proposal is prompted

by issuance of mandatory continuing

airworthiness information by a foreign

civil airworthiness authority. The

actions specified by the proposed AD

are intended to detect and correct

desynchronization of the rudder servo

actuators, which could result in reduced

structural integrity of the rudder

attachments and reduced controllability

of the airplane.

DATES: Effective July 30, 1998.

The incorporation by reference of

certain publications listed in the

regulations is approved by the Director

of the Federal Register as of July 30,

1998.

ADDRESSES: The service information

referenced in this AD may be obtained

from Airbus Industrie, 1 Rond Point

Maurice Bellonte, 31707 Blagnac Cedex,

France. This information may be

examined at the Federal Aviation

Administration (FAA), Transport

Airplane Directorate, Rules Docket,

1601 Lind Avenue, SW., Renton,

Washington; or at the Office of the

Federal Register, 800 North Capitol

Street, NW., suite 700, Washington, DC.

FOR FURTHER INFORMATION CONTACT:

Norman B. Martenson, Manager,

International Branch, ANM–116, FAA,

Transport Airplane Directorate, 1601

Lind Avenue, SW., Renton, Washington

98055–4056; telephone (425) 227–2110;

fax (425) 227–1149.

SUPPLEMENTARY INFORMATION: A

proposal to amend part 39 of the Federal

Aviation Regulations (14 CFR part 39) to

include an airworthiness directive (AD)

that is applicable to all Airbus Model

A300, A300–600, and A310 series

airplanes was published in the Federal

Register on March 6, 1998 (63 FR

11169). That action proposed to require

repetitive tests to detect

desynchronization of the rudder servo

actuators, and adjustment or

replacement of the spring rods of the

rudder servo actuators, if necessary. For

certain airplanes, this AD also requires

repetitive inspections to detect cracking

of the rudder attachments, and repair, if

necessary; or modification of the rudder

attachments.

Interested persons have been afforded

an opportunity to participate in the

making of this amendment. Due

consideration has been given to the

comments received.

Revise the Cost Information

The Air Transport Association (ATA)

of America, on behalf of one of its

members, requests that the cost estimate

presented in the proposal be revised.

The ATA states that the data contained

in the proposal does not take into

consideration the costs required for

actions that may be required as a result

of certain inspection findings.

The FAA does not concur that the

cost estimate information should be

revised. The economic analysis of the

AD is limited only to the cost of actions

that are actually required by the rule. It

does not consider the costs of ‘‘on

condition’’ actions, such as adjustments

or replacement of parts if a discrepancy

is detected during a required inspection.

Such ‘‘on condition’’ actions would be

required to be accomplished—regardless

of AD direction—in order to correct an

identified unsafe condition, and to

ensure operation of that airplane in an

airworthy condition, as required by the

Federal Aviation Regulations.

Conclusion

After careful review of the available

data, including the comment noted

above, the FAA has determined that air

safety and the public interest require the

adoption of the rule as proposed.

Cost Impact

The FAA estimates that 103 Airbus

Model A300, A300–600, and A310

series airplanes of U.S. registry will be

affected by this proposed AD, that it

will take approximately 1 work hour per

airplane to accomplish the proposed

test, and that the average labor rate is

$60 per work hour. Based on these

figures, the cost impact of the AD on

U.S. operators is estimated to be $60 per

airplane, per test cycle.

The cost impact figure discussed

above is based on assumptions that no

operator has yet accomplished any of

the requirements of this AD action, and

that no operator would accomplish

those actions in the future if this AD

were not adopted.

Regulatory Impact

The regulations adopted herein will

not have substantial direct effects on the

States, on the relationship between the

national government and the States, or

on the distribution of power and

responsibilities among the various

levels of government. Therefore, in

accordance with Executive Order 12612,

it is determined that this final rule does

not have sufficient federalism

implications to warrant the preparation

of a Federalism Assessment.

For the reasons discussed above, I

certify that this action (1) is not a

‘‘significant regulatory action’’ under

Executive Order 12866; (2) is not a

‘‘significant rule’’ under DOT

Regulatory Policies and Procedures (44

FR 11034, February 26, 1979); and (3)

will not have a significant economic

impact, positive or negative, on a

substantial number of small entities

under the criteria of the Regulatory

Flexibility Act. A final evaluation has

been prepared for this action and it is

contained in the Rules Docket. A copy

of it may be obtained from the Rules

Docket at the location provided under

the caption ADDRESSES.

List of Subjects in 14 CFR Part 39

Air transportation, Aircraft, Aviation

safety, Incorporation by reference,

Safety.
Federal Register / Vol. 63, No. 122 /Thursday, June 25, 1998 /Rules and Regulations 34581

Adoption of the Amendment

Accordingly, pursuant to the

authority delegated to me by the

Administrator, the Federal Aviation

Administration amends part 39 of the

Federal Aviation Regulations (14 CFR

part 39) as follows:

PART 39—AIRWORTHINESS

DIRECTIVES

1. The authority citation for part 39

continues to read as follows:

Authority: 49 U.S.C. 106(g), 40113, 44701.

§ 39.13 [Amended]

2. Section 39.13 is amended by

adding the following new airworthiness

directive:

98–13–33 Airbus Industrie: Amendment

39–10624. Docket 97–NM–257–AD.

Applicability: All Model A300, A300–600,

and A310 series airplanes, certificated in any

category.

Note 1: This AD applies to each airplane

identified in the preceding applicability

provision, regardless of whether it has been

modified, altered, or repaired in the area

subject to the requirements of this AD. For

airplanes that have been modified, altered, or

repaired so that the performance of the

requirements of this AD is affected, the

owner/operator must request approval for an

alternative method of compliance in

accordance with paragraph (d) of this AD.

The request should include an assessment of

the effect of the modification, alteration, or

repair on the unsafe condition addressed by

this AD; and, if the unsafe condition has not

been eliminated, the request should include

specific proposed actions to address it.

Compliance: Required as indicated, unless

accomplished previously.

To detect and correct desynchronization of

the rudder servo actuators, which could

result in reduced structural integrity of the

rudder attachments and reduced

controllability of the airplane, accomplish

the following:

(a) Prior to accumulation of 1,300 total

flight hours, or within 500 flight hours after

the effective date of this AD, whichever

occurs later, and thereafter at intervals not to

exceed 1,300 flight hours: Perform a test to

detect desynchronization of the rudder servo

actuators in accordance with Airbus Service

Bulletin A300–27–0188, Revision 2, dated

October 1, 1997 (for Model A300 series

airplanes); A300–27–6036, Revision 2, dated

October 1, 1997 (for Model A300–600 series

airplanes); or A310–27–2082, Revision 2,

dated October 1, 1997 (for Model A310 series

airplanes); as applicable. If any

desynchronization (rudder movement) is

detected, prior to further flight, either adjust

or replace, as applicable, the spring rod of the

affected rudder servo actuator in accordance

with the applicable service bulletin.

Note 2: A test to detect desynchronization

of the rudder servo actuators, if

accomplished prior to the effective date of

this AD in accordance with Airbus Service

Bulletin A300–27–0188, dated October 24,

1996, or Revision 1, dated November 5, 1996

(for Model A300 series airplanes); A300–27–

6036, dated October 24, 1996, or Revision 1,

dated November 5, 1996 (for Model A300–

600 series airplanes); or A310–27–2082,

dated October 24, 1996, or Revision 1, dated

November 5, 1996 (for Model A310 series

airplanes); is considered acceptable for

compliance with the initial test required by

paragraph (a) of this AD.

(b) Except as provided by paragraph (c) of

this AD, if any desynchronization (rudder

movement) greater than the limit specified in

Paragraph B of the Accomplishment

Instructions of the applicable service bulletin

is detected during any test required by

paragraph (a), prior to further flight,

accomplish either paragraph (b)(1) or (b)(2) of

this AD, in accordance with Airbus Service

Bulletin A300–55–0044, dated October 22,

1996 (for Model A300 series airplanes);

A300–55–6023, dated October 22, 1996 (for

Model A300–600 series airplanes); or A310–

55–2026, dated October 22, 1996 (for Model

A310 series airplanes); as applicable.

(1) Conduct a visual inspection, high

frequency eddy current inspection, or

ultrasonic inspection, as applicable, to detect

cracking of the rudder attachments; and

repeat the inspection thereafter, as

applicable, at the intervals specified in the

applicable service bulletin. Or

(2) Modify the rudder attachments to cold

expand the rivet holes.

(c) If any crack is found during any

inspection or modification required by

paragraph (b) of this AD, and the applicable

service bulletin specifies to contact Airbus

for an appropriate action: Prior to further

flight, repair the affected structure in

accordance with a method approved by the

Manager, International Branch, ANM–116,

FAA, Transport Airplane Directorate, or in

accordance with a method approved by the

Direction Generale de l’Aviation Civile

(DGAC), which is the airworthiness authority

for France.

(d) An alternative method of compliance or

adjustment of the compliance time that

provides an acceptable level of safety may be

used if approved by the Manager,

International Branch, ANM–116. Operators

shall submit their requests through an

appropriate FAA Principal Maintenance

Inspector, who may add comments and then

send it to the Manager, International Branch,

ANM–116.

Note 3: Information concerning the

existence of approved alternative methods of

compliance with this AD, if any, may be

obtained from the International Branch,

ANM–116.

(e) Special flight permits may be issued in

accordance with sections 21.197 and 21.199

of the Federal Aviation Regulations (14 CFR

21.197 and 21.199) to operate the airplane to

a location where the requirements of this AD

can be accomplished.

(f) Except as provided in paragraph (c) of

this AD, the repetitive inspections and repair

shall be done in accordance with Airbus

Service Bulletin A300–55–0044, dated

October 22, 1996; Airbus Service Bulletin

A300–55–6023, dated October 22, 1996; or

Airbus Service Bulletin A310–55–2026,

dated October 22, 1996, as applicable.

Testing for desynchronization shall be done

in accordance with Airbus Service Bulletin

A300–27–0188, Revision 2, dated October 1,

1997; Airbus Service Bulletin A300–27–6036,

Revision 2, dated October 1, 1997; or Airbus

Service Bulletin A310–27–2082, Revision 2,

dated October 1, 1997, as applicable. This

incorporation by reference was approved by

the Director of the Federal Register in

accordance with 5 U.S.C. 552(a) and 1 CFR

part 51. Copies may be obtained from Airbus

Industrie, 1 Rond Point Maurice Bellonte,

31707 Blagnac Cedex, France. Copies may be

inspected at the FAA, Transport Airplane

Directorate, 1601 Lind Avenue, SW., Renton,

Washington; or at the Office of the Federal

Register, 800 North Capitol Street, NW., suite

700, Washington, DC.

Note 4: The subject of this AD is addressed

in French airworthiness directive 96–242–

208(B) R2, dated November 19, 1997.

(g) This amendment becomes effective on

July 30, 1998.

Issued in Renton, Washington, on June 16,

1998.

Darrell M. Pederson,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 98–16491 Filed 6–24–98; 8:45 am]

BILLING CODE 4910–13–U

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 97–NM–329–AD; Amendment

39–10623; AD 98–13–32]

RIN 2120–AA64

Airworthiness Directives; Fokker

Model F.28 Mark 0100 Series Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment adopts a

new airworthiness directive (AD),

applicable to certain Fokker Model F.28

Mark 0100 series airplanes, that requires

interim inspections to detect

discrepancies of the main fitting

subassembly of the main landing gear,

and follow-on corrective actions, if

necessary. This amendment also

requires a one-time inspection to detect

discrepancies of the fitting, repair of the

fitting, if necessary, and application of

new surface protection on the fitting,

which would terminate the interim

inspections. This amendment is

prompted by issuance of mandatory

continuing airworthiness information by

a foreign civil airworthiness authority.

The actions specified by this AD are

intended to prevent cracking of the

main fitting subassembly of the main

landing gear, which could result in

collapse of the main landing gear.